Transactions of Nanjing University of Aeronautics & Astronautics
Nonlinear Control Method for Hypersonic Vehicle Based on Double Power Reaching Law of Sliding Mode
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Abstract:
The intelligence nonlinear control scheme via double power reaching law based sliding mode control method is proposed to solve the problems of model uncertainties and unknown outside disturbances. Firstly, the aerodynamic parameters of the morphing vehicle are replaced with curve-fitted approximation to build the accurate model for control design in the hypersonic flight. Then the nonlinear vehicle model is transformed into the strict feedback multi-input/multi-output nonlinear system by using the input-output feedback linearization approach. At the same time, the disturbance observer is used to approximate the unknown disturbance, and the sliding mode method is used to solve the problem of non-matching and uncertainty. Finally, according to the buffeting problem in sliding mode control, the double power is improved. Simulation results show that the proposed method can ensure the global stability of the closed-loop system, and has good tracking and robust performance.
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Project Supported:
This work was supported by the Advanced Research Foundation of Ministry of Army Equipment Development in 13th Five-Year (No.30102080101), the Aviation Science Funds (No.20165852052), and the Fundamental Research Funds for the Central Universities (No.NS2018059).
Clc Number:
TN247
CHINA AERO-SCIENCES
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